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DF102 (df102-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: DF102 (df102-il)
Reynolds number: 200,000
Max Cl/Cd: 56.27 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-df102-il-200000-n5.txt
Download as CSV file: xf-df102-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DF102                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6299   0.06251   0.05850  -0.0531   1.0000   0.0129
 -11.000  -0.6479   0.05514   0.05103  -0.0597   1.0000   0.0127
 -10.750  -0.6679   0.04920   0.04492  -0.0649   1.0000   0.0127
 -10.500  -0.6949   0.04509   0.04054  -0.0653   1.0000   0.0129
 -10.250  -0.7090   0.04267   0.03802  -0.0626   1.0000   0.0127
 -10.000  -0.7243   0.03983   0.03484  -0.0596   1.0000   0.0129
  -9.750  -0.7309   0.03745   0.03226  -0.0565   1.0000   0.0131
  -9.500  -0.7327   0.03549   0.03013  -0.0535   1.0000   0.0133
  -9.250  -0.7317   0.03385   0.02834  -0.0505   1.0000   0.0135
  -9.000  -0.7288   0.03230   0.02662  -0.0474   1.0000   0.0137
  -8.750  -0.7202   0.03066   0.02478  -0.0454   0.9992   0.0140
  -8.500  -0.6938   0.02864   0.02248  -0.0467   0.9948   0.0146
  -8.250  -0.6677   0.02676   0.02031  -0.0476   0.9902   0.0153
  -8.000  -0.6398   0.02500   0.01827  -0.0485   0.9858   0.0160
  -7.750  -0.6085   0.02368   0.01661  -0.0498   0.9825   0.0171
  -7.500  -0.5830   0.02231   0.01522  -0.0502   0.9772   0.0181
  -7.250  -0.5525   0.02136   0.01418  -0.0513   0.9731   0.0196
  -7.000  -0.5201   0.02024   0.01290  -0.0527   0.9701   0.0209
  -6.750  -0.4922   0.01934   0.01186  -0.0529   0.9648   0.0220
  -6.500  -0.4631   0.01826   0.01076  -0.0537   0.9602   0.0239
  -6.250  -0.4302   0.01757   0.00999  -0.0551   0.9568   0.0265
  -6.000  -0.4021   0.01688   0.00919  -0.0552   0.9511   0.0286
  -5.750  -0.3734   0.01614   0.00843  -0.0557   0.9456   0.0316
  -5.500  -0.3407   0.01560   0.00777  -0.0567   0.9418   0.0354
  -5.250  -0.3146   0.01500   0.00713  -0.0564   0.9348   0.0395
  -5.000  -0.2848   0.01446   0.00656  -0.0568   0.9293   0.0475
  -4.750  -0.2561   0.01381   0.00599  -0.0571   0.9239   0.0685
  -4.500  -0.2309   0.01318   0.00557  -0.0567   0.9164   0.1148
  -4.250  -0.2010   0.01273   0.00527  -0.0572   0.9114   0.1599
  -4.000  -0.1757   0.01247   0.00508  -0.0566   0.9029   0.1899
  -3.750  -0.1464   0.01221   0.00486  -0.0568   0.8970   0.2168
  -3.500  -0.1207   0.01199   0.00472  -0.0563   0.8885   0.2499
  -3.250  -0.0925   0.01176   0.00455  -0.0562   0.8819   0.2790
  -3.000  -0.0665   0.01159   0.00439  -0.0557   0.8729   0.2974
  -2.750  -0.0381   0.01139   0.00417  -0.0556   0.8661   0.3146
  -2.500  -0.0126   0.01122   0.00403  -0.0549   0.8563   0.3324
  -2.250   0.0146   0.01103   0.00387  -0.0546   0.8482   0.3527
  -2.000   0.0410   0.01085   0.00372  -0.0541   0.8389   0.3760
  -1.750   0.0670   0.01067   0.00360  -0.0536   0.8294   0.4033
  -1.500   0.0937   0.01046   0.00347  -0.0531   0.8207   0.4369
  -1.250   0.1187   0.01025   0.00339  -0.0524   0.8101   0.4786
  -1.000   0.1437   0.01003   0.00333  -0.0516   0.7999   0.5306
  -0.750   0.1683   0.00978   0.00326  -0.0506   0.7879   0.5911
  -0.500   0.1921   0.00953   0.00318  -0.0493   0.7728   0.6555
  -0.250   0.2158   0.00929   0.00314  -0.0478   0.7555   0.7262
   0.000   0.2430   0.00912   0.00316  -0.0469   0.7380   0.8096
   0.250   0.2822   0.00911   0.00318  -0.0485   0.7191   0.8845
   0.500   0.3197   0.00918   0.00316  -0.0500   0.6991   0.9253
   0.750   0.3573   0.00927   0.00313  -0.0517   0.6766   0.9498
   1.000   0.3936   0.00938   0.00311  -0.0532   0.6551   0.9675
   1.250   0.4325   0.00948   0.00311  -0.0553   0.6345   0.9806
   1.500   0.4719   0.00960   0.00309  -0.0577   0.6122   0.9914
   1.750   0.5090   0.00972   0.00310  -0.0597   0.5870   1.0000
   2.000   0.5308   0.00988   0.00314  -0.0584   0.5642   1.0000
   2.250   0.5522   0.01007   0.00319  -0.0571   0.5377   1.0000
   2.500   0.5732   0.01029   0.00327  -0.0556   0.5067   1.0000
   2.750   0.5936   0.01055   0.00336  -0.0542   0.4704   1.0000
   3.000   0.6129   0.01090   0.00349  -0.0525   0.4257   1.0000
   3.250   0.6308   0.01135   0.00367  -0.0507   0.3729   1.0000
   3.500   0.6484   0.01187   0.00390  -0.0488   0.3192   1.0000
   3.750   0.6667   0.01238   0.00417  -0.0472   0.2795   1.0000
   4.000   0.6861   0.01282   0.00446  -0.0457   0.2540   1.0000
   4.250   0.7065   0.01321   0.00474  -0.0444   0.2355   1.0000
   4.500   0.7274   0.01358   0.00503  -0.0431   0.2216   1.0000
   4.750   0.7483   0.01395   0.00533  -0.0419   0.2106   1.0000
   5.000   0.7702   0.01426   0.00564  -0.0408   0.2009   1.0000
   5.250   0.7917   0.01461   0.00596  -0.0397   0.1926   1.0000
   5.500   0.8132   0.01497   0.00628  -0.0386   0.1841   1.0000
   5.750   0.8350   0.01532   0.00662  -0.0375   0.1767   1.0000
   6.000   0.8564   0.01569   0.00698  -0.0365   0.1696   1.0000
   6.250   0.8780   0.01606   0.00736  -0.0354   0.1639   1.0000
   6.500   0.8998   0.01642   0.00774  -0.0344   0.1583   1.0000
   6.750   0.9204   0.01687   0.00816  -0.0332   0.1534   1.0000
   7.000   0.9421   0.01725   0.00860  -0.0322   0.1488   1.0000
   7.250   0.9634   0.01765   0.00904  -0.0312   0.1441   1.0000
   7.500   0.9834   0.01813   0.00950  -0.0300   0.1396   1.0000
   7.750   1.0044   0.01856   0.00998  -0.0289   0.1356   1.0000
   8.000   1.0253   0.01899   0.01049  -0.0278   0.1316   1.0000
   8.250   1.0453   0.01947   0.01101  -0.0267   0.1283   1.0000
   8.500   1.0639   0.02007   0.01159  -0.0253   0.1252   1.0000
   8.750   1.0841   0.02057   0.01217  -0.0242   0.1225   1.0000
   9.000   1.1041   0.02107   0.01277  -0.0230   0.1194   1.0000
   9.250   1.1232   0.02158   0.01337  -0.0218   0.1163   1.0000
   9.500   1.1409   0.02216   0.01397  -0.0204   0.1135   1.0000
   9.750   1.1574   0.02286   0.01468  -0.0189   0.1112   1.0000
  10.000   1.1755   0.02343   0.01539  -0.0175   0.1092   1.0000
  10.250   1.1928   0.02404   0.01612  -0.0160   0.1069   1.0000
  10.500   1.2091   0.02466   0.01686  -0.0145   0.1044   1.0000
  10.750   1.2242   0.02527   0.01755  -0.0128   0.1019   1.0000
  11.000   1.2376   0.02600   0.01829  -0.0110   0.0992   1.0000
  11.250   1.2523   0.02669   0.01912  -0.0095   0.0964   1.0000
  11.500   1.2659   0.02723   0.01981  -0.0079   0.0922   1.0000
  11.750   1.2772   0.02785   0.02049  -0.0062   0.0880   1.0000
  12.000   1.2887   0.02865   0.02138  -0.0046   0.0842   1.0000
  12.250   1.3022   0.02937   0.02228  -0.0033   0.0801   1.0000
  12.500   1.3129   0.03025   0.02323  -0.0018   0.0761   1.0000
  12.750   1.3229   0.03125   0.02433  -0.0004   0.0723   1.0000
  13.000   1.3351   0.03217   0.02540   0.0007   0.0666   1.0000
  13.250   1.3438   0.03335   0.02665   0.0019   0.0610   1.0000
  13.500   1.3519   0.03467   0.02803   0.0029   0.0531   1.0000
  13.750   1.3575   0.03629   0.02971   0.0040   0.0449   1.0000
  14.000   1.3575   0.03847   0.03192   0.0051   0.0359   1.0000
  14.250   1.3539   0.04112   0.03459   0.0060   0.0290   1.0000
  14.500   1.3471   0.04423   0.03777   0.0065   0.0240   1.0000
  14.750   1.3390   0.04767   0.04132   0.0067   0.0213   1.0000
  15.000   1.3309   0.05131   0.04511   0.0065   0.0194   1.0000
  15.250   1.3194   0.05559   0.04954   0.0057   0.0180   1.0000
  15.500   1.3060   0.06040   0.05451   0.0043   0.0173   1.0000
  15.750   1.2895   0.06604   0.06032   0.0022   0.0165   1.0000
  16.000   1.2728   0.07212   0.06660  -0.0005   0.0162   1.0000
  16.250   1.2520   0.07934   0.07402  -0.0041   0.0161   1.0000
  16.500   1.2270   0.08783   0.08273  -0.0087   0.0162   1.0000
  16.750   1.1942   0.09852   0.09365  -0.0146   0.0168   1.0000
  17.000   1.1646   0.10897   0.10433  -0.0204   0.0176   1.0000
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